US20210395473A1 - Anaerobic composite matrix resins - Google Patents
Anaerobic composite matrix resins Download PDFInfo
- Publication number
- US20210395473A1 US20210395473A1 US17/409,185 US202117409185A US2021395473A1 US 20210395473 A1 US20210395473 A1 US 20210395473A1 US 202117409185 A US202117409185 A US 202117409185A US 2021395473 A1 US2021395473 A1 US 2021395473A1
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- United States
- Prior art keywords
- resin
- matrix
- primer
- composite
- treated
- Prior art date
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- Pending
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- 239000011347 resin Substances 0.000 title claims abstract description 148
- 229920005989 resin Polymers 0.000 title claims abstract description 148
- 239000011159 matrix material Substances 0.000 title claims abstract description 58
- 239000002131 composite material Substances 0.000 title claims description 68
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 61
- 239000004917 carbon fiber Substances 0.000 claims abstract description 61
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 61
- 230000002787 reinforcement Effects 0.000 claims abstract description 35
- 238000000034 method Methods 0.000 claims abstract description 27
- 239000000463 material Substances 0.000 claims abstract description 20
- 230000008439 repair process Effects 0.000 claims description 32
- YMWUJEATGCHHMB-UHFFFAOYSA-N Dichloromethane Chemical compound ClCCl YMWUJEATGCHHMB-UHFFFAOYSA-N 0.000 claims description 30
- NIXOWILDQLNWCW-UHFFFAOYSA-M Acrylate Chemical compound [O-]C(=O)C=C NIXOWILDQLNWCW-UHFFFAOYSA-M 0.000 claims description 17
- 239000003795 chemical substances by application Substances 0.000 claims description 17
- 239000000243 solution Substances 0.000 claims description 16
- 238000004513 sizing Methods 0.000 claims description 14
- ZKXWKVVCCTZOLD-UHFFFAOYSA-N copper;4-hydroxypent-3-en-2-one Chemical group [Cu].CC(O)=CC(C)=O.CC(O)=CC(C)=O ZKXWKVVCCTZOLD-UHFFFAOYSA-N 0.000 claims description 13
- SJECZPVISLOESU-UHFFFAOYSA-N 3-trimethoxysilylpropan-1-amine Chemical compound CO[Si](OC)(OC)CCCN SJECZPVISLOESU-UHFFFAOYSA-N 0.000 claims description 11
- CERQOIWHTDAKMF-UHFFFAOYSA-N Methacrylic acid Chemical compound CC(=C)C(O)=O CERQOIWHTDAKMF-UHFFFAOYSA-N 0.000 claims description 11
- CVHZOJJKTDOEJC-UHFFFAOYSA-N saccharin Chemical compound C1=CC=C2C(=O)NS(=O)(=O)C2=C1 CVHZOJJKTDOEJC-UHFFFAOYSA-N 0.000 claims description 11
- 235000019204 saccharin Nutrition 0.000 claims description 11
- JLTDJTHDQAWBAV-UHFFFAOYSA-N N,N-dimethylaniline Chemical compound CN(C)C1=CC=CC=C1 JLTDJTHDQAWBAV-UHFFFAOYSA-N 0.000 claims description 10
- UHESRSKEBRADOO-UHFFFAOYSA-N ethyl carbamate;prop-2-enoic acid Chemical compound OC(=O)C=C.CCOC(N)=O UHESRSKEBRADOO-UHFFFAOYSA-N 0.000 claims description 9
- KCTAWXVAICEBSD-UHFFFAOYSA-N prop-2-enoyloxy prop-2-eneperoxoate Chemical compound C=CC(=O)OOOC(=O)C=C KCTAWXVAICEBSD-UHFFFAOYSA-N 0.000 claims description 9
- FRIBMENBGGCKPD-UHFFFAOYSA-N 3-(2,3-dimethoxyphenyl)prop-2-enal Chemical compound COC1=CC=CC(C=CC=O)=C1OC FRIBMENBGGCKPD-UHFFFAOYSA-N 0.000 claims description 8
- IAXXETNIOYFMLW-COPLHBTASA-N [(1s,3s,4s)-4,7,7-trimethyl-3-bicyclo[2.2.1]heptanyl] 2-methylprop-2-enoate Chemical compound C1C[C@]2(C)[C@@H](OC(=O)C(=C)C)C[C@H]1C2(C)C IAXXETNIOYFMLW-COPLHBTASA-N 0.000 claims description 8
- 239000012190 activator Substances 0.000 claims description 8
- 125000003118 aryl group Chemical group 0.000 claims description 8
- 239000003054 catalyst Substances 0.000 claims description 8
- DEETYPHYGZQVKD-UHFFFAOYSA-N copper ethyl hexanoate Chemical group [Cu+2].CCCCCC(=O)OCC DEETYPHYGZQVKD-UHFFFAOYSA-N 0.000 claims description 8
- 229940119545 isobornyl methacrylate Drugs 0.000 claims description 8
- GNSFRPWPOGYVLO-UHFFFAOYSA-N 3-hydroxypropyl 2-methylprop-2-enoate Chemical compound CC(=C)C(=O)OCCCO GNSFRPWPOGYVLO-UHFFFAOYSA-N 0.000 claims description 7
- 150000004982 aromatic amines Chemical class 0.000 claims description 7
- 239000012745 toughening agent Substances 0.000 claims description 7
- 239000003999 initiator Substances 0.000 claims description 6
- YIJYFLXQHDOQGW-UHFFFAOYSA-N 2-[2,4,6-trioxo-3,5-bis(2-prop-2-enoyloxyethyl)-1,3,5-triazinan-1-yl]ethyl prop-2-enoate Chemical compound C=CC(=O)OCCN1C(=O)N(CCOC(=O)C=C)C(=O)N(CCOC(=O)C=C)C1=O YIJYFLXQHDOQGW-UHFFFAOYSA-N 0.000 claims description 5
- SBITWGSPHGZZAG-UHFFFAOYSA-N 2-methylprop-2-enoic acid prop-2-enenitrile Chemical compound CC(C(=O)O)=C.CC(C(=O)O)=C.C(C=C)#N SBITWGSPHGZZAG-UHFFFAOYSA-N 0.000 claims description 5
- ZWEHNKRNPOVVGH-UHFFFAOYSA-N Methyl ethyl ketone Natural products CCC(C)=O ZWEHNKRNPOVVGH-UHFFFAOYSA-N 0.000 claims description 5
- 229920003006 Polybutadiene acrylonitrile Polymers 0.000 claims description 5
- 150000002978 peroxides Chemical class 0.000 claims description 5
- VEBCLRKUSAGCDF-UHFFFAOYSA-N ac1mi23b Chemical compound C1C2C3C(COC(=O)C=C)CCC3C1C(COC(=O)C=C)C2 VEBCLRKUSAGCDF-UHFFFAOYSA-N 0.000 claims description 4
- GGSUCNLOZRCGPQ-UHFFFAOYSA-N diethylaniline Chemical compound CCN(CC)C1=CC=CC=C1 GGSUCNLOZRCGPQ-UHFFFAOYSA-N 0.000 claims description 4
- 239000011152 fibreglass Substances 0.000 claims description 4
- 229920002681 hypalon Polymers 0.000 claims description 4
- 150000002902 organometallic compounds Chemical class 0.000 claims description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 4
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 claims description 3
- UICBCXONCUFSOI-UHFFFAOYSA-N n'-phenylacetohydrazide Chemical compound CC(=O)NNC1=CC=CC=C1 UICBCXONCUFSOI-UHFFFAOYSA-N 0.000 claims description 3
- 239000010453 quartz Substances 0.000 claims description 3
- JUVSRZCUMWZBFK-UHFFFAOYSA-N 2-[n-(2-hydroxyethyl)-4-methylanilino]ethanol Chemical compound CC1=CC=C(N(CCO)CCO)C=C1 JUVSRZCUMWZBFK-UHFFFAOYSA-N 0.000 claims description 2
- ZTKDMNHEQMILPE-UHFFFAOYSA-N 4-methoxy-n,n-dimethylaniline Chemical compound COC1=CC=C(N(C)C)C=C1 ZTKDMNHEQMILPE-UHFFFAOYSA-N 0.000 claims description 2
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- SPTHWAJJMLCAQF-UHFFFAOYSA-M ctk4f8481 Chemical compound [O-]O.CC(C)C1=CC=CC=C1C(C)C SPTHWAJJMLCAQF-UHFFFAOYSA-M 0.000 claims description 2
- JDEJGVSZUIJWBM-UHFFFAOYSA-N n,n,2-trimethylaniline Chemical compound CN(C)C1=CC=CC=C1C JDEJGVSZUIJWBM-UHFFFAOYSA-N 0.000 claims description 2
- GYVGXEWAOAAJEU-UHFFFAOYSA-N n,n,4-trimethylaniline Chemical compound CN(C)C1=CC=C(C)C=C1 GYVGXEWAOAAJEU-UHFFFAOYSA-N 0.000 claims description 2
- HKJNHYJTVPWVGV-UHFFFAOYSA-N n,n-diethyl-4-methylaniline Chemical compound CCN(CC)C1=CC=C(C)C=C1 HKJNHYJTVPWVGV-UHFFFAOYSA-N 0.000 claims description 2
- WMOVHXAZOJBABW-UHFFFAOYSA-N tert-butyl acetate Chemical compound CC(=O)OC(C)(C)C WMOVHXAZOJBABW-UHFFFAOYSA-N 0.000 claims description 2
- CIHOLLKRGTVIJN-UHFFFAOYSA-N tert‐butyl hydroperoxide Chemical compound CC(C)(C)OO CIHOLLKRGTVIJN-UHFFFAOYSA-N 0.000 claims description 2
- MEUKEBNAABNAEX-UHFFFAOYSA-N hydroperoxymethane Chemical group COO MEUKEBNAABNAEX-UHFFFAOYSA-N 0.000 claims 1
- 230000009477 glass transition Effects 0.000 abstract description 12
- 230000008569 process Effects 0.000 abstract description 9
- 238000009734 composite fabrication Methods 0.000 abstract description 7
- 238000001721 transfer moulding Methods 0.000 abstract description 7
- 238000010438 heat treatment Methods 0.000 abstract description 5
- 239000004593 Epoxy Substances 0.000 abstract description 4
- 238000009726 composite fabrication method Methods 0.000 abstract description 3
- 230000008030 elimination Effects 0.000 abstract description 3
- 238000003379 elimination reaction Methods 0.000 abstract description 3
- 239000003733 fiber-reinforced composite Substances 0.000 abstract description 3
- 239000011342 resin composition Substances 0.000 abstract description 2
- 238000013036 cure process Methods 0.000 abstract 1
- 229920001187 thermosetting polymer Polymers 0.000 abstract 1
- 239000004925 Acrylic resin Substances 0.000 description 39
- 238000012360 testing method Methods 0.000 description 25
- 239000000835 fiber Substances 0.000 description 24
- 239000004744 fabric Substances 0.000 description 22
- 238000001723 curing Methods 0.000 description 15
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- 238000009472 formulation Methods 0.000 description 13
- 239000000758 substrate Substances 0.000 description 13
- 239000000178 monomer Substances 0.000 description 12
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 10
- 239000001301 oxygen Substances 0.000 description 10
- 229910052760 oxygen Inorganic materials 0.000 description 10
- 229910052751 metal Inorganic materials 0.000 description 9
- 239000002184 metal Substances 0.000 description 9
- 239000011800 void material Substances 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 6
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- 239000000901 saccharin and its Na,K and Ca salt Substances 0.000 description 6
- 239000002904 solvent Substances 0.000 description 6
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 5
- -1 acrylate ester Chemical class 0.000 description 5
- 229910052802 copper Inorganic materials 0.000 description 5
- 239000010949 copper Substances 0.000 description 5
- 238000007655 standard test method Methods 0.000 description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 4
- LCXXNKZQVOXMEH-UHFFFAOYSA-N Tetrahydrofurfuryl methacrylate Chemical compound CC(=C)C(=O)OCC1CCCO1 LCXXNKZQVOXMEH-UHFFFAOYSA-N 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 4
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- 238000002411 thermogravimetry Methods 0.000 description 4
- 229910052723 transition metal Inorganic materials 0.000 description 4
- 150000003624 transition metals Chemical class 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- VVQNEPGJFQJSBK-UHFFFAOYSA-N Methyl methacrylate Chemical compound COC(=O)C(C)=C VVQNEPGJFQJSBK-UHFFFAOYSA-N 0.000 description 3
- BLRPTPMANUNPDV-UHFFFAOYSA-N Silane Chemical compound [SiH4] BLRPTPMANUNPDV-UHFFFAOYSA-N 0.000 description 3
- 230000003213 activating effect Effects 0.000 description 3
- 239000000654 additive Substances 0.000 description 3
- QUZSUMLPWDHKCJ-UHFFFAOYSA-N bisphenol A dimethacrylate Chemical compound C1=CC(OC(=O)C(=C)C)=CC=C1C(C)(C)C1=CC=C(OC(=O)C(C)=C)C=C1 QUZSUMLPWDHKCJ-UHFFFAOYSA-N 0.000 description 3
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- 238000009736 wetting Methods 0.000 description 3
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 2
- QIGBRXMKCJKVMJ-UHFFFAOYSA-N Hydroquinone Chemical compound OC1=CC=C(O)C=C1 QIGBRXMKCJKVMJ-UHFFFAOYSA-N 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000005062 Polybutadiene Substances 0.000 description 2
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- WYTZZXDRDKSJID-UHFFFAOYSA-N (3-aminopropyl)triethoxysilane Chemical compound CCO[Si](OCC)(OCC)CCCN WYTZZXDRDKSJID-UHFFFAOYSA-N 0.000 description 1
- BPXVHIRIPLPOPT-UHFFFAOYSA-N 1,3,5-tris(2-hydroxyethyl)-1,3,5-triazinane-2,4,6-trione Chemical compound OCCN1C(=O)N(CCO)C(=O)N(CCO)C1=O BPXVHIRIPLPOPT-UHFFFAOYSA-N 0.000 description 1
- KFDNQUWMBLVQNB-UHFFFAOYSA-N 2-[2-[bis(carboxymethyl)amino]ethyl-(carboxymethyl)amino]acetic acid;sodium Chemical compound [Na].[Na].[Na].[Na].OC(=O)CN(CC(O)=O)CCN(CC(O)=O)CC(O)=O KFDNQUWMBLVQNB-UHFFFAOYSA-N 0.000 description 1
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- 125000000954 2-hydroxyethyl group Chemical group [H]C([*])([H])C([H])([H])O[H] 0.000 description 1
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- LSXJOKPZCYULKN-UHFFFAOYSA-N 3-hydroxypropyl 2-methylprop-2-enoate;prop-2-enenitrile Chemical compound C=CC#N.CC(=C)C(=O)OCCCO LSXJOKPZCYULKN-UHFFFAOYSA-N 0.000 description 1
- NLHHRLWOUZZQLW-UHFFFAOYSA-N Acrylonitrile Chemical compound C=CC#N NLHHRLWOUZZQLW-UHFFFAOYSA-N 0.000 description 1
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- VNZQQAVATKSIBR-UHFFFAOYSA-L copper;octanoate Chemical compound [Cu+2].CCCCCCCC([O-])=O.CCCCCCCC([O-])=O VNZQQAVATKSIBR-UHFFFAOYSA-L 0.000 description 1
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- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
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Images
Classifications
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Definitions
- the present disclosure pertains to novel composite materials useful for composite repair and composite part fabrication.
- Tg delivered glass transition temperature
- Matrix resins for elevated temperature composite applications typically have two-components that require mixing, or are pre-impregnated on the fiber reinforcement. The pre-impregnated versions suffer from short shelf-life and must be stored at sub-ambient temperatures to prevent premature gellation of the resin system. Elevated Tg matrix resins commonly have excessive viscosities, which require heating during processing to reduce viscosity and maximize consolidation with the fiber reinforcement.
- High temperature laminating resins often require elevated temperature curing. Resins with elevated Tg that cure at ambient temperatures have previously been developed that cure via ultraviolet light (UV). However, these UV curing acrylate resins are limited to use with fiberglass or quartz fabrics. Their efficacy with carbon fiber reinforcements is problematic due to the strong UV absorption of the carbon.
- the present disclosure pertains to low viscosity ambient temperature curing composite matrix resin systems that eliminates the need for heating to achieve cure. Compared to previous resin technologies, the composite resin system will cure completely when carbon fiber is used as the reinforcement. The resin is also compatible with fiberglass and quartz reinforcements.
- the resins have the potential to reduce costs currently associated with composite fabrication.
- the resin system can be used for original composite part fabrication or for repair of damaged composite parts. With regards to the latter, the matrix resins developed will provide repairs having equivalent strength, while reducing the support equipment and man-hours per repair.
- the resin system developed can be cured at ambient temperatures. Without postcure the resin will provide a glass transition temperature more than 350° F. (177° C.).
- the resulting composites also exhibit high fiber strength translation. The implications are significant in terms of the ease of use and elimination of procedural steps. While the resin system was developed specifically for vacuum bagging, it is expected to be viable for other composite fabrication methods including out of autoclave (OOA), resin transfer molding (RTM) and vacuum-assisted resin transfer molding (VARTM).
- OOA autoclave
- RTM resin transfer molding
- VARTM vacuum-assisted resin transfer molding
- one embodiment is a stable prepreg material (i.e., fabric reinforcement that has been “pre-impregnated” with a resin system) that will only cure after application to the repair area when under vacuum bagging conditions, which removes oxygen and allows cure of the part at ambient temperatures.
- Anaerobically curing matrix resins for composite applications has not been investigated.
- the reason for this lack of research in the use of anaerobic resins for composites is likely due to the absence of metal ions on the surface of common reinforcements.
- the matrix resin technology described herein is based on an anaerobic curing approach that will potentially transform not only composite repairs, but several composite fabrication areas in general. Embodiments of the technology have been demonstrated whereby a unique sizing agent system is used to treat reinforcements with organometallic compounds, which serve as catalysts in the anaerobic reaction.
- a unique sizing agent system is used to treat reinforcements with organometallic compounds, which serve as catalysts in the anaerobic reaction.
- cure is not initiated until the impregnated fabric is exposed to an oxygen free atmosphere. This occurs during the vacuum bagging process, where the resin cures to a rigid cross-linked network at ambient temperatures.
- the curing agent package which composes less than 5% of the formulation in preferred embodiments, is based on the proper balance of aromatic amine(s) and hydroperoxides, and saccharin.
- the curing agent package may include combinations of peroxide initiators, such as cumene hydroperoxide, aromatic amine accelerators, and benzoic sulfimide (saccharin). Additional preferred embodiments also use a cure promoter/silane adhesion promoter applied to the carbon fiber fabric reinforcement.
- peroxide initiators such as cumene hydroperoxide, aromatic amine accelerators, and benzoic sulfimide (saccharin).
- Additional preferred embodiments also use a cure promoter/silane adhesion promoter applied to the carbon fiber fabric reinforcement.
- FIG. 1 shows the anaerobic cure profile for a preferred embodiment of a resin system with carbon fiber reinforcement and promoter solution at 23° C.
- FIG. 2 shows the effect of promoter concentration applied to fiber on cure time at 23° C. with a preferred embodiment of a resin system.
- FIG. 3 shows a 20 ply AS4/plain weave carbon fiber laminate produced using a preferred embodiment of an anaerobic epoxy acrylate matrix resin.
- FIG. 4 shows a cross section of cured plain weave carbon fiber laminate produced using a preferred embodiment of an anaerobic epoxy acrylate matrix resin.
- FIG. 5 shows a simulated repair performed on 2.0 in. Honeycomb sandwich composite.
- FIG. 6 shows a complete repair panel fabricated with treated plain weave carbon fiber and a preferred embodiment of a matrix resin.
- FIG. 7 shows the short beam shear results for IM7 unidirectional composite prepared with a preferred embodiment of an anaerobic resin.
- FIG. 8 shows the glass transition temperature for a preferred embodiment of a resin system reinforced with carbon fiber.
- FIG. 9 shows the glass transition temperature for a commercially available resin reinforced with carbon fiber after cure.
- FIG. 10 shows the thermal stability of a preferred embodiment of a resin and a standard epoxy resin composite with plain weave carbon fiber fabric.
- FIG. 11 shows photomicrographs of a composite cross section using a preferred embodiment of a resin.
- FIG. 12 shows photomicrographs of a composite cross section using a commercially available resin.
- FIG. 13 shows the results for the anaerobic cure profile at 73° F. for AC-5911 Resin System/IM7 Carbon Fiber (2% promoter on fiber).
- FIG. 14 shows flexural modulus vs. temperature for AC-5911 Resin System/IM7 Carbon Fiber.
- the present disclosure relates to anaerobically curing composite resin systems.
- the system is composed of acrylate based resin materials and curing agents that promote cure under anaerobic conditions.
- the system is composed of acrylate based resin materials and a primer including a catalyst.
- An additional preferable aspect involves treatment of the fiber reinforcement with an organometallic catalyst sizing system, also referred to as a promoter/silane adhesion promoter solution, or activator sizing agent.
- the treated reinforcement is therefore rendered a part of the curing mechanism.
- the composite system is designed to cure only when the resin comes into contact with the fiber reinforcement and is in an anaerobic state. Such anaerobic conditions commonly occur in composite fabrication methods such as vacuum bag molding and closed molding.
- Anaerobic ally curing resins commonly contain a free-radically polymerizable acrylate ester monomer, together with a peroxy initiator and an inhibitor component. Often, such anaerobic resins also contain accelerator components to increase the cure speed of the composition.
- the basic components in preferred embodiments of the matrix resin include acrylate based resin materials, including acrylate monomers and polymers blended to provide the desired mechanical and thermal properties.
- Useful acrylates include monomers and oligomers derived from bisphenol-A dimethacrylate, hydrogenated bisphenol-A dimethacrylate, and ethoxylated bisphenol-A dimethacrylate. These include polybutadiene dimethacrylate and polybutadiene acrylonitrile dimethacrylate, also referred to as methacrylate-functional butadiene copolymer.
- the acrylonitrile content in the polybutadiene acrylonitrile dimethacrylate is about 21-22, or preferably 21.5, percent.
- Additional preferred monomers and oligomers may be derived from methyl methacrylate, methacrylic acid, tris (2-hydroxy ethyl) isocyanurate triacrylate, Isobornyl methacrylate, tetrahydrofurfuryl methacrylate, hydroxypropyl methacrylate, tricyclodecane dimethanol diacrylate, and hexafunctional aromatic urethane acrylate.
- Various useful urethane-acrylate type monomers include those derived from chemical linking of precursor “prepolymers” then “capping” with (meth)acrylate.
- the curing agent package may include combinations of peroxide initiators, such as cumene hydroperoxide, aromatic amine accelerators, and benzoic sulfimide (saccharin).
- peroxide initiators include one or more of cumene hydroperoxide, t-butylhydroperoxide, p-methane hydroperoxide, diisopropylbenzene hydroperoxide, pinene hydroperoxide, and methyl ethyl ketone peroxide.
- Common initiators include one or more of cumene hydroperoxide, t-butylhydroperoxide, p-methane hydroperoxide, diisopropylbenzene hydroperoxide, pinene hydroperoxide, and methyl ethyl ketone peroxide.
- Anaerobic cure-inducing compounds to accelerate cure can include saccharin and an aromatic amine.
- Examples of preferable aromatic amines include one or more of N,N-diethyl-p-toluidine, N,N-dimethyl-o-toluidine, and acetyl phenylhydrazine (APH), N,N-dimethylaniline, N,N-dimethyl-p-toluidine, N,N-dimethyl-p-anisidine, N,N-diethylaniline, and N,N-bis-(2-hydroxyethyl)-p-toluidine.
- APH acetyl phenylhydrazine
- stabilizers are typically added to prevent premature polymerization.
- the addition of stabilizers is important to maximize long-term room temperature stability.
- Preferred stabilizers include chelators such as tetrasodium ethylenediamine tetraacetic acid to scavenge extraneous metal ions.
- Radical inhibitor additives may also be included in the formulation, such as hydroquinone or naphthoquinone.
- Additives for viscosity control include fumed silica, also known as pyrogenic silica.
- the composite materials can be produced by conventional manufacturing processes that are capable of anaerobic conditions. These processes include Resin Transfer Molding (RTM), Vacuum Assisted Resin Transfer Molding (VARTM), vacuum bag molding, and filament winding.
- RTM Resin Transfer Molding
- VARTM Vacuum Assisted Resin Transfer Molding
- filament winding filament winding
- One preferred embodiment is the use of the anaerobic resin system with carbon fiber reinforcements that have been treated with compounds to facilitate cure and adhesion of the matrix resin.
- a solution containing accelerators and adhesion promoters can be used as a fiber sizing agent for the carbon fiber.
- the accelerator/adhesion promoter solution is applied to the carbon fiber and allowed to dry, leaving residual accelerator/ adhesion promoter coating in the form of organometallic compounds on the reinforcement material.
- the amount of accelerator/adhesion promoter composition that adheres to the carbon fiber is preferably in the range of 0.1 to 5 percent based on the weight of the carbon fiber.
- transition metal ions include copper, manganese, chromium, iron, cobalt, nickel, and molybdenum. More preferred is copper.
- the oxidation state of the transition metal is not crucial, but the lower oxidation state which can be oxidized is rather preferred.
- the transition metal compound may be in the form of an inorganic or organometallic compound, including oxides, salts, and organometallic chelates and complexes. Appropriate inorganic salts include the sulfates, nitrates, chlorides, bromides, phosphates, and sulfides.
- Suitable organic salts include the alkoxides, including methoxides and ethoxides, as well as the carboxylates, including the acetates, hexoates, octoates, ethylhexanoates, and naphthenates.
- Other suitable transition metal complexes include the acetylacetonates and the hexafluoroacetylacetonates. More preferably, the transition metal compound is selected from the group consisting of copper acetylacetonate, copper ethylhexanoate, copper acetate, copper naphthenate, copper octoate, copper hexoate, and copper hexafluoroacetylacetonate. Most preferably, the transition metal compound is copper acetylacetonate.
- Preferred adhesion promoters include amino silanes, such as gamma-aminopropyltrimethoxy silane, gamma-aminopropyltriethoxy silane, N-(betaaminoethyl)-gamma-aminopropyltriethoxy silane, and the like.
- amino silanes such as gamma-aminopropyltrimethoxy silane, gamma-aminopropyltriethoxy silane, N-(betaaminoethyl)-gamma-aminopropyltriethoxy silane, and the like.
- organo silanes can be utilized as well as the corresponding silanols and polysiloxanes.
- accelerator/adhesion promoter adhesion promoter solution or activator sizing agent
- accelerator/adhesion promoter adhesion promoter solution includes copper acetylacetonate (2% w/w) and gamma-aminopropyltrimethoxy silane (1%) in methylene chloride. Lower concentrations of both the accelerator and adhesion promoter were found to be effective.
- the preferred range for the accelerator component is 0.2 to 5% weight in solution.
- the preferred range for the adhesion promoter is 0.1 to 3 percent by weight in solution.
- Additional preferred embodiments utilize an anaerobic primer system to improve adhesion to cured composite substrates.
- the primer was designed to interact with the cured composite substrate to improve adhesion. In addition, it increases the cure rate of the anaerobic matrix resin at the interface.
- the primer is applied to the prepared substrate before the impregnated repair plies are applied.
- the carbon fiber in the repair plies will already contain the metal activating sizing agent to promote rapid cure.
- the primer will also contain a metal activating cure promoter to increase the cure rate at the interfaces between the cured laminate and the repair laminate.
- Structural composite sections where repairs are typically applied, can be considered to be relatively non-polar in nature (compared to some polymers and metals).
- Polarity of the substrate affects its surface energy, which is what enables the matrix resin to wet out the substrate.
- the primer include a solvent, one or more acrylate based resin materials, one or more additional elastomeric materials, and a catalyst of accelerator including a transition metal.
- the solvent may include tertiary butyl acetate, for substrate wetting, and the one or more acrylate based resin materials may include monomers and/or oligomers derived from, for example, hydroxypropyl methacrylate, isobornyl methacrylate, hexafunctional aromatic urethane acrylate, and methacrylic acid. These acrylate resin materials function to promote adhesion to the carbon fiber and substrate, increase hydrophobicity, serve as a toughener, and increase reactivity.
- One or more additional elastomer materials such as chlorsulfonated polyethylene, which functions as a toughener, may also be present.
- Preferred embodiments of the primer may also include copper ethylhexanoate as a catalyst.
- the hydroxypropyl methacrylate improves chemical adhesion by a hydrogen bonding mechanism through the hydroxyl groups.
- Isobornyl methacrylate acts as a diluent, but also improves the thermal properties and adhesion.
- the methacrylic acid and urethane acrylate are intended to increase reactivity and crosslink density of the cured primer.
- the copper ethylhexanoate is incorporated to promote the anaerobic cure rate at the bonded interfaces.
- the primer also incorporates an elastomeric toughener, chlorosulfonated polyethylene, and copper ethylhexanoate to accelerate the anerobic cure rate.
- the primer can be used in conjunction with matrix resins prepared in accordance with preferred embodiments described herein.
- Preferred embodiments described herein are preferably used as a matrix resin for carbon fiber reinforced composites.
- the types of carbon fiber that can be used with this resin include unidirectional and woven products. These carbon fiber reinforcements are available from several manufacturers including Toray Industries Inc., Toho Tenax Co. Ltd., U.S., Zoltek Companies Inc., and Hexcel Corp.
- the preferred curing method involves inducing an anaerobic state around the impregnated carbon fiber reinforcement.
- Some composite fabrication techniques employ vacuum assistance as part of the impregnation and compaction process. The use of vacuum inherently produces an anaerobic state, wherein the materials of the present invention would be viable. Examples of this include vacuum bag molding and resin transfer molding. Other composite fabrication techniques could be modified to introduce an anaerobic state, either by use of vacuum or purging the process equipment or molds with a gas that is oxygen-free.
- Carbon fiber reinforcement cloth used in the following examples was Hexcel style 282 made with AS4 input fiber.
- Combinations of the acrylate monomers and oligomers listed in Table 1 can be used in preferred embodiments of the matrix resin.
- One particularly advantageous preferred embodiment of a resin formulation is described in Table 2 below.
- This Example resin system was designated internally as AC-1291. It contains methyl methacrylate, methacrylic acid, epoxy acrylate, tris (2-hydroxyethyl) isocyanurate triacrylate, hexafunctional aromatic urethane acrylate, and isobornyl methacrylate.
- the curing agent components included saccharin, N,N-dimethylaniline, and cumene hydroperoxide.
- HEXCEL Stamford, Conn.
- HEXTOW IM7 carbon fiber was treated with a solution of gamma aminopropyltrimethoxy silane (1% w/w) and copper acetylacetonate (2% w/w) dissolved in methylene chloride. The solvent was allowed to evaporate from the carbon fiber, thus leaving an activated sizing component on the reinforcement. Eighteen strands of the treated carbon fiber reinforcement were then pulled into a thin flexible tube. The tube was then injected with the anaerobic epoxy acrylate resin (AC-1291), while fixtured in a dynamic mechanical analyzer (DMA). The dynamic modulus of the composite was measured at room temperature until no additional increase in modulus was observed.
- FIG. 1 shows the cure study results, the anaerobic cure profile for AC-1291 resin system with IM7 carbon fiber (2% promoter on fiber) at 73° F.
- the cure rate was found to be very rapid when the copper acetylacetonate accelerator concentration in the fiber treatment was 2 percent, showing a cure onset of approximately 3 minutes.
- the specimen achieved full cure at room temperature within one hour of combining the anaerobic resin and activating carbon fiber fabric. After ambient temperature cure the glass transition temperature for this composite was determined to be 360° F. (182° C.) using DMA in the flexural mode.
- FIG. 2 shows the effect of varying promoter level (applied to fiber) on level of cure at 73° F. for AC-1291, which is expressed as conversion relative to the ultimate modulus on the plot.
- Woven carbon fiber fabric (HEXCEL HEXTOW AS4) was pretreated with a sizing containing 0.5 percent copper acetylacetonate accelerator and 1.0 percent gamma aminopropyltrimethoxy silane (adhesion promoter) dissolved in methylene chloride. After evaporation of the solvent, five plies of the woven carbon fiber fabric were impregnated with resin AC-1291 and debulked/cured in a vacuum bag for thirty minutes. The laminate which was approximately 4 inches square was allowed to cure for thirty minutes under vacuum. The exotherm was measured with a thermocouple and the maximum temperature recorded was 65° C. Larger panels were subsequently prepared using this same process.
- the resin used for these trials was the preferred anaerobic resin AC-1291. No heating blankets were required and the laminate was simply cured by removal of oxygen during the vacuum bagging procedure.
- the AS4 carbon fiber was treated with the activator sizing agent (0.2% copper acetylacetonate (accelerator) and 1.0% gamma aminopropyltrimethoxy silane dissolved in methylene chloride. In this case the CuAcAC concentration was reduced to 0.2% in order to provide additional working time and to reduce excess exotherm.
- FIG. 3 shows the composite laminate prepared with the developed resin (AC-1291) and 20 plies of AS4 plain weave carbon fiber fabric.
- FIG. 4 is a photograph of the cured laminate cross section.
- Composite sandwich panels are composed of thin, high strength composite skins separated by and bonded to lightweight honeycomb cores. These structures are commonly repaired on aircraft and require additional steps to ensure that mechanical properties are restored to the damaged area.
- a simulated 0.5 inch thick sandwich panel repair was prepared by cutting a 2.5 in diameter circular area from one of the laminate sides. Five AS4 carbon fiber patches, previously treated with activator, were cut to fill the void, and one final patch was applied that was approximately two inches larger in diameter. Each fabric patch was wet-out with AC-1291 resin. A second simulated repair was performed on a 2.0 inch thick sandwich panel using the same basic materials and process. A photograph of this cured repair after debagging is shown in FIG. 5 .
- Laminate repair simulations were performed using previously prepared epoxy/carbon fiber flat panels, 3 ft. ⁇ 1 ft. ⁇ 0.168 in. An 8-inch diameter circular area was abraded in the middle of each panel, using a 90 degree die grinder and Scotchbrite pads. Plain weave AS4 carbon fiber cloth, that was previously treated with activator (0.2%), then cut into circular repair plies.
- the circular plies were used to lay-up two simulated repairs, using a “wedding cake” stack configuration to simulate surface doubler repairs.
- a tapered scarf repair would typically be done, with the repair plies laid with the smallest ply down first, then the next smallest ply, and so on, with the largest ply being the top repair ply.
- the previously abraded composite area was wet out with the AC-1291 resin, followed by laying the 7-inch diameter ply into the wet resin and additional resin on top of the ply, using the stiff short-bristle brush to work the resin down through the thickness of the ply. After thoroughly wetting out the first ply, additional resin was applied to wet out the subsequent ply. This process was repeated for all succeeding plies, with the 1-inch circular ply being applied last. Care was taken to ensure that all plies were thoroughly saturated with resin. All plies were laid up as symmetrical 0°/90° plain weave plies, to match the original structure.
- the two sets of repair plies were wet out in the same way, from the same batch of mixed resin. Up to this point, the two repairs were treated identically.
- the difference between the two repair panels involved the vacuum bag bleeder schedules used. Panel 1 was bagged with an aggressive bleeder schedule, designed to pull out excess resin under vacuum.
- Panel 1 was connected to vacuum approximately 30 minutes prior to vacuum being applied to Panel 2.
- the vacuum pressure was maintained at 24 in Hg to extract air from both bags.
- Panel 1 was under full vacuum for 3 hours, and Panel 2 was under full vacuum for 2.5 hours. No thermal cure was required. When the panels were debagged, the resin appeared to be fully cured, and was hard to the touch, with no trace of tackiness.
- Panel 2 had a more resin rich surface compared to Panel 1. This was attributed to the more conservative bleeder schedule used for Panel 2. Photographs of the cured repair laminates are shown in FIG. 6 .
- Interlaminar shear strength (ILSS) tests were performed according to ASTM Test Method D2344, Standard Test Method for Short-Beam Strength of Polymer Matrix Composite Materials and Their Laminates (astm.org/Standards/D2344.htm). Specimens were prepared using the AC-1291 resin system with IM7 carbon fiber reinforcement that was previously treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane. The carbon fiber was wet-out using AC-1291 anaerobic resin.
- the individual ILSS specimens were positioned in an Instron test machine in a three point bend configuration. Support span was 0.63 inches, and the crosshead speed was 0.05 inches per minute. The maximum load was used to calculate the interlaminar shear strength.
- FIG. 7 shows short beam shear results for IM7 unidirectional composite prepared with anaerobic resin AC-1291.
- the data presented in FIG. 7 shows that the AC-1291 matrix resin can deliver strengths comparable to laminates prepared with the standard EA-9390 matrix resin.
- An average ILSS of 8,570 psi was obtained.
- Flexural properties were determined for the anaerobically cured composite prepared with 20 plies of AS4 carbon fiber fabric.
- the fabric was treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane.
- the carbon fiber was wet-out using AC-1291 anaerobic resin.
- a vacuum bag assembly was used to remove oxygen from the bagged laminate to promote cure. Vacuum was maintained for one hour at ambient temperature.
- Lap-Shear Strength The level of adhesion of the anaerobic matrix resin to cured composite laminates was determined.
- One inch wide strips were cut from a previously cured carbon fiber reinforced (CFR) composite which was prepared with AC-1291 resin and 10 plies of AS4 carbon fiber fabric.
- the fabric was treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane.
- the carbon fiber was wet-out using AC-1291 anaerobic resin.
- a vacuum bag assembly was used to remove oxygen from the bagged laminate to promote cure. Vacuum was maintained for one hour at ambient temperature. Cured specimens having dimensions of 6 in. ⁇ 1 in. ⁇ 0.10 in. were cut from the resulting laminate panel.
- the cured one-inch wide composite strips were abraded with 120 grit sandpaper followed by cleaning by wiping with methyl ethyl ketone.
- the cleaned strips were then treated with a methylene chloride primer solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane.
- AC-1291 anaerobic resin was applied to a one square inch area of each cured laminate strip adherend.
- a fiberglass scrim cloth was applied to maintain the bondline thickness to 0.010 inches. Two of the strips were then adhered to each other over the one square inch area. The anaerobic cure was allowed to proceed for twenty four hours. After cure, the samples were tested for lap-shear adhesion on an Instron test machine.
- the lap-shear tests were performed according to ASTM D5868 Standard Test Method for Lap Shear Adhesion for Fiber Reinforced Plastic (FRP) (astm.org/Standards/D5868). The results for the tests, which were performed at 73° F., with a crosshead speed of 0.05 inches per minute, are described in Table 4. The average lap-shear strength observed was 1,451 psi.
- Dynamic mechanical analysis testing was performed to determine the mechanical properties of cured laminates over a temperature range.
- Specimens were prepared with anaerobic resin (AC-1291) and treated AS4 plain weave carbon fiber fabric.
- a composite panel was prepared with AC-1291 resin and 10 plies of AS4 carbon fiber fabric.
- the fabric was treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane.
- the carbon fiber was wet-out using AC-1291 anaerobic resin.
- a vacuum bag assembly was used to remove oxygen from the bagged laminate to promote cure. Vacuum was maintained for one hour at ambient temperature. Cured specimens having dimensions of 1.2 in. ⁇ 0.4 in. ⁇ 0.1 in. were cut from the resulting laminate panel.
- FIG. 8 shows the DMA results obtained, or the glass transition temperature for the AC-1291 resin system reinforced with AS4 carbon fiber (2% promoter on fiber).
- a similar composite was prepared and tested using EA-9390 conventional epoxy matrix resin as shown in FIG. 9 .
- FIG. 9 shows dynamic mechanical analyses results for EA-9390 resin reinforced with AS4 carbon fiber; Tg after cure at 250° F. (121° C.).
- the glass transition temperature observed for the anaerobic was comparable to that of the composite fabricated with a standard HENKEL (Bay Point, CA) HYSOL EA-9390 resin, a two-component epoxy adhesive designed for composite repair. Both test laminates exhibited Tg's of approximately 360° F. (182° C.).
- Thermogravimetric analysis was performed using a TA Instruments Model 2950 Analyzer. Samples of the composites prepared as described in [0062]. However, the specimens for TGA tests were cut to dimensions of 0.1 in. ⁇ 0.1 in. ⁇ 0.1 in. Specimens were placed in a tared platinum pan and heated at a rate of 10° C. per minute (5.5° F. per minute) to 600° C. (1,112° F.). The tests were performed in a nitrogen atmosphere.
- FIG. 10 shows thermal stability of AC-1291 Resin and standard EA-9390 epoxy resin composites; 20 ply construction with AS4 plain weave carbon fiber fabric. The weight loss plots in FIG.
- Void content testing of the composites was determined according to ASTM D2734, Standard Test Methods for Void Content of Reinforced Plastics (astm.org/Standards/D2734).
- the measured density of composite specimens was determined by the dry/wet weight method ASTM D792 Method A, Standard Test Methods for Density and Specific Gravity (Relative Density) of Plastics by Displacement (astm.org/Standards/D792).
- FIG. 11 shows photomicrographs of AC-1291/AS4 20 ply composite cross sections.
- FIG. 12 shows photomicrographs of EA-9390/AS4 20 ply composite cross sections.
- the composite prepared with EA-9390 had a significantly higher level of porosity compared to the AC-1291 laminate.
- Tables 6 and 7 below provide details regarding the exemplary primer formulation and matrix resin formulations that were prepared and evaluated.
- the ambient temperature curing behavior of anaerobic matrix resin AC-5911 was determined by impregnating IM7-12K carbon fiber tow, which was previously sized with a dilute solution of the promoter/silane adhesion promoter. The sizing agent solution was applied to the carbon fiber and allowed to dry leaving residual promoter on the reinforcement. Eighteen strands of the reinforcement were then wet-out with the resin, then fixtured in a dynamic mechanical analyzer (DMA). The dynamic modulus of the composite was measured at room temperature until no additional increase in modulus was observed.
- FIG. 13 shows the results for the anaerobic cure profile at 73° F. for AC-5911 Resin System/IM7 Carbon Fiber (2% promoter on fiber).
- This resin system achieved full cure at room temperature within one hour of fabrication. After ambient cure the glass transition temperature for this composite was determined to be 377° F. (192° C.) using DMA in the flexural mode, as shown in FIG. 14 . This Tg is significantly higher compared to previous matrix resins developed.
- Interlaminar Shear Strength Tests were determined according to ASTM Test Method D 2344. This test, commonly known as the short-beam strength (SBS) test, attempts to quantify the interlaminar (out-of-plane) shear strength of parallel fiber reinforced composites. Table 9 below contains the ILSS data obtained with composite specimens prepared with matrix resin AC-5911. The substitution of the polybutadiene dimethacrylate with polybutadiene acrylonitrile dimethacrylate significantly increased the ILSS compared to the previously tested anaerobic resin compositions.
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Abstract
A matrix resin composition for fiber reinforced composite materials is described. The resin is thermosetting and achieves a glass transition temperature of at least 177° C. (Tg), obtained by curing under anaerobic conditions at room temperature. The matrix resin will streamline composite fabrication processes by eliminating the need for heating during the cure process. The implications of this development are significant in terms of the ease of use and elimination of procedural steps. While the resin system was developed specifically for vacuum bagging, it is expected to be viable for other composite fabrication methods including resin transfer molding (RTM) and vacuum-assisted resin transfer molding (VARTM). The resin system is viable for use with carbon fiber reinforcements to fabricate laminates at least 0.20 inches thick. The resulting laminates have low porosity and mechanical properties equivalent to those prepared with common epoxy matrix resins.
Description
- This application is a divisional of U.S. patent application Ser. No. 16/173,570, which is a continuation-in-part of and claims priority to U.S. patent application Ser. No. 16/157,386, filed Oct. 11, 2018, entitled “Anaerobic Composite Matrix Resins,” which claims priority to U.S. Provisional Patent Application No. 62/571,349, filed Oct. 12, 2017, entitled “Anaerobic Composite Matrix Resins.” The entire contents of the foregoing applications are hereby incorporated by reference.
- The present disclosure pertains to novel composite materials useful for composite repair and composite part fabrication.
- This invention was made with government support under Contract No. N68335-16-C-0242 awarded by the U.S. Navy, Naval Air Systems Command. The government has certain rights in the invention.
- Materials and techniques for fabrication of fiber reinforced composite materials that exhibit elevated temperature performance have several limitations. A common measure of thermal performance is the delivered glass transition temperature (Tg) of the fabricated composite. Matrix resins for elevated temperature composite applications typically have two-components that require mixing, or are pre-impregnated on the fiber reinforcement. The pre-impregnated versions suffer from short shelf-life and must be stored at sub-ambient temperatures to prevent premature gellation of the resin system. Elevated Tg matrix resins commonly have excessive viscosities, which require heating during processing to reduce viscosity and maximize consolidation with the fiber reinforcement.
- High temperature laminating resins often require elevated temperature curing. Resins with elevated Tg that cure at ambient temperatures have previously been developed that cure via ultraviolet light (UV). However, these UV curing acrylate resins are limited to use with fiberglass or quartz fabrics. Their efficacy with carbon fiber reinforcements is problematic due to the strong UV absorption of the carbon.
- What is needed is a composite fabrication system that does not require heat or UV energy to initiate cure, yet that delivers composites capable of high temperature service conditions.
- The present disclosure pertains to low viscosity ambient temperature curing composite matrix resin systems that eliminates the need for heating to achieve cure. Compared to previous resin technologies, the composite resin system will cure completely when carbon fiber is used as the reinforcement. The resin is also compatible with fiberglass and quartz reinforcements.
- The resins have the potential to reduce costs currently associated with composite fabrication. The resin system can be used for original composite part fabrication or for repair of damaged composite parts. With regards to the latter, the matrix resins developed will provide repairs having equivalent strength, while reducing the support equipment and man-hours per repair. The resin system developed can be cured at ambient temperatures. Without postcure the resin will provide a glass transition temperature more than 350° F. (177° C.). The resulting composites also exhibit high fiber strength translation. The implications are significant in terms of the ease of use and elimination of procedural steps. While the resin system was developed specifically for vacuum bagging, it is expected to be viable for other composite fabrication methods including out of autoclave (OOA), resin transfer molding (RTM) and vacuum-assisted resin transfer molding (VARTM).
- Acrylate based resin systems were formulated to cure anaerobically. The result is a resin that is stable at room temperature for months in the presence of atmospheric oxygen. Therefore, one embodiment is a stable prepreg material (i.e., fabric reinforcement that has been “pre-impregnated” with a resin system) that will only cure after application to the repair area when under vacuum bagging conditions, which removes oxygen and allows cure of the part at ambient temperatures.
- Resins that cure anaerobically were first discovered in the 1940's, when it was found that acrylate based adhesives formulated with specific curatives, form metal-to-metal bonds in the absence of oxygen. A key factor in the cure mechanism is the need for metal catalysis. For metal bonding applications, the catalytic metal is supplied at the substrate interface. Copper and iron are well known to increase kinetics of reaction whereas cadmium or zinc are inactive. After the adhesive is applied, which removes access to oxygen, peroxides form free radicals under the catalytic effect of metal ions.
- Anaerobically curing matrix resins for composite applications has not been investigated. The reason for this lack of research in the use of anaerobic resins for composites is likely due to the absence of metal ions on the surface of common reinforcements.
- The matrix resin technology described herein is based on an anaerobic curing approach that will potentially transform not only composite repairs, but several composite fabrication areas in general. Embodiments of the technology have been demonstrated whereby a unique sizing agent system is used to treat reinforcements with organometallic compounds, which serve as catalysts in the anaerobic reaction. When the formulated matrix resin is applied to the treated reinforcement, cure is not initiated until the impregnated fabric is exposed to an oxygen free atmosphere. This occurs during the vacuum bagging process, where the resin cures to a rigid cross-linked network at ambient temperatures. The curing agent package, which composes less than 5% of the formulation in preferred embodiments, is based on the proper balance of aromatic amine(s) and hydroperoxides, and saccharin. The curing agent package may include combinations of peroxide initiators, such as cumene hydroperoxide, aromatic amine accelerators, and benzoic sulfimide (saccharin). Additional preferred embodiments also use a cure promoter/silane adhesion promoter applied to the carbon fiber fabric reinforcement.
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FIG. 1 shows the anaerobic cure profile for a preferred embodiment of a resin system with carbon fiber reinforcement and promoter solution at 23° C. -
FIG. 2 shows the effect of promoter concentration applied to fiber on cure time at 23° C. with a preferred embodiment of a resin system. -
FIG. 3 shows a 20 ply AS4/plain weave carbon fiber laminate produced using a preferred embodiment of an anaerobic epoxy acrylate matrix resin. -
FIG. 4 shows a cross section of cured plain weave carbon fiber laminate produced using a preferred embodiment of an anaerobic epoxy acrylate matrix resin. -
FIG. 5 shows a simulated repair performed on 2.0 in. Honeycomb sandwich composite. -
FIG. 6 shows a complete repair panel fabricated with treated plain weave carbon fiber and a preferred embodiment of a matrix resin. -
FIG. 7 shows the short beam shear results for IM7 unidirectional composite prepared with a preferred embodiment of an anaerobic resin. -
FIG. 8 shows the glass transition temperature for a preferred embodiment of a resin system reinforced with carbon fiber. -
FIG. 9 shows the glass transition temperature for a commercially available resin reinforced with carbon fiber after cure. -
FIG. 10 shows the thermal stability of a preferred embodiment of a resin and a standard epoxy resin composite with plain weave carbon fiber fabric. -
FIG. 11 shows photomicrographs of a composite cross section using a preferred embodiment of a resin. -
FIG. 12 shows photomicrographs of a composite cross section using a commercially available resin. -
FIG. 13 shows the results for the anaerobic cure profile at 73° F. for AC-5911 Resin System/IM7 Carbon Fiber (2% promoter on fiber). -
FIG. 14 shows flexural modulus vs. temperature for AC-5911 Resin System/IM7 Carbon Fiber. - The present disclosure relates to anaerobically curing composite resin systems. Preferably, the system is composed of acrylate based resin materials and curing agents that promote cure under anaerobic conditions. In certain embodiments the system is composed of acrylate based resin materials and a primer including a catalyst. An additional preferable aspect involves treatment of the fiber reinforcement with an organometallic catalyst sizing system, also referred to as a promoter/silane adhesion promoter solution, or activator sizing agent. The treated reinforcement is therefore rendered a part of the curing mechanism. The composite system is designed to cure only when the resin comes into contact with the fiber reinforcement and is in an anaerobic state. Such anaerobic conditions commonly occur in composite fabrication methods such as vacuum bag molding and closed molding.
- Anaerobic ally curing resins commonly contain a free-radically polymerizable acrylate ester monomer, together with a peroxy initiator and an inhibitor component. Often, such anaerobic resins also contain accelerator components to increase the cure speed of the composition.
- The basic components in preferred embodiments of the matrix resin include acrylate based resin materials, including acrylate monomers and polymers blended to provide the desired mechanical and thermal properties. Useful acrylates include monomers and oligomers derived from bisphenol-A dimethacrylate, hydrogenated bisphenol-A dimethacrylate, and ethoxylated bisphenol-A dimethacrylate. These include polybutadiene dimethacrylate and polybutadiene acrylonitrile dimethacrylate, also referred to as methacrylate-functional butadiene copolymer. In preferred embodiments, the acrylonitrile content in the polybutadiene acrylonitrile dimethacrylate is about 21-22, or preferably 21.5, percent. Additional preferred monomers and oligomers may be derived from methyl methacrylate, methacrylic acid, tris (2-hydroxy ethyl) isocyanurate triacrylate, Isobornyl methacrylate, tetrahydrofurfuryl methacrylate, hydroxypropyl methacrylate, tricyclodecane dimethanol diacrylate, and hexafunctional aromatic urethane acrylate. Various useful urethane-acrylate type monomers include those derived from chemical linking of precursor “prepolymers” then “capping” with (meth)acrylate.
- A description of examples of preferred acrylate monomers and oligomers used for formulation of preferred embodiments of the matrix resins is shown in Table 1 below.
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TABLE 1 ACRYLATE MONOMERS AND OLIGOMERS Description/ Resin [Commercial Product Component Number] Structure Epoxy acrylate oligomer Imparts flexibility, excellent adhesion, and low shrinkage [CN UVE 151, Sartomer (Exton, PA)] Tris (2- hydroxy ethyl)iso- cyanurate triacrylate Fast cure response, adhesion, weatherability, high impact strength, low shrinkage and hardness. [SR368, Sartomer] Isobornyl methacrylate Excellent reactive diluent for oligomers. The cyclic group produces polymers through free radical curing which have a high glass transition temperature. [SR423A, Sartomer] Hexafunctional aromatic urethane acrylate oligomer A hexafunctional aromatic urethane acrylate oligomer with excellent cure response, low viscosity, and very high crosslink density. [CN975, Sartomer] Tetrahydro- furfuryl methacrylate (THFMA) Monofunctional methacrylate monomer offers low viscosity, low shrinkage, high hardness, high solvency, good adhesion, good balance of mechanical properties Tricyclodecane Dimethanol Diacrylate Low viscosity difunctional acrylate monomer that provides high Tg, high flexibility, and low shrinkage. - The curing agent package may include combinations of peroxide initiators, such as cumene hydroperoxide, aromatic amine accelerators, and benzoic sulfimide (saccharin). Common initiators include one or more of cumene hydroperoxide, t-butylhydroperoxide, p-methane hydroperoxide, diisopropylbenzene hydroperoxide, pinene hydroperoxide, and methyl ethyl ketone peroxide. Anaerobic cure-inducing compounds to accelerate cure can include saccharin and an aromatic amine. Examples of preferable aromatic amines include one or more of N,N-diethyl-p-toluidine, N,N-dimethyl-o-toluidine, and acetyl phenylhydrazine (APH), N,N-dimethylaniline, N,N-dimethyl-p-toluidine, N,N-dimethyl-p-anisidine, N,N-diethylaniline, and N,N-bis-(2-hydroxyethyl)-p-toluidine.
- Various additives can be added to the resin formulation, and stabilizers are typically added to prevent premature polymerization. The addition of stabilizers is important to maximize long-term room temperature stability. Preferred stabilizers include chelators such as tetrasodium ethylenediamine tetraacetic acid to scavenge extraneous metal ions. Radical inhibitor additives may also be included in the formulation, such as hydroquinone or naphthoquinone. Additives for viscosity control include fumed silica, also known as pyrogenic silica.
- The composite materials can be produced by conventional manufacturing processes that are capable of anaerobic conditions. These processes include Resin Transfer Molding (RTM), Vacuum Assisted Resin Transfer Molding (VARTM), vacuum bag molding, and filament winding. However, compared to previous state of the art materials, these new materials do not require elevated temperature cure to achieve the desired high glass transition temperatures. Thus, the cost associated with heating equipment and energy usage is expected to be lower compared to conventional composite materials.
- One preferred embodiment is the use of the anaerobic resin system with carbon fiber reinforcements that have been treated with compounds to facilitate cure and adhesion of the matrix resin. A solution containing accelerators and adhesion promoters can be used as a fiber sizing agent for the carbon fiber. The accelerator/adhesion promoter solution is applied to the carbon fiber and allowed to dry, leaving residual accelerator/ adhesion promoter coating in the form of organometallic compounds on the reinforcement material. After evaporation, the amount of accelerator/adhesion promoter composition that adheres to the carbon fiber is preferably in the range of 0.1 to 5 percent based on the weight of the carbon fiber.
- Particularly suitable accelerators include compounds containing transition metal ions. Preferred transition metals include copper, manganese, chromium, iron, cobalt, nickel, and molybdenum. More preferred is copper. The oxidation state of the transition metal is not crucial, but the lower oxidation state which can be oxidized is rather preferred. The transition metal compound may be in the form of an inorganic or organometallic compound, including oxides, salts, and organometallic chelates and complexes. Appropriate inorganic salts include the sulfates, nitrates, chlorides, bromides, phosphates, and sulfides. Suitable organic salts include the alkoxides, including methoxides and ethoxides, as well as the carboxylates, including the acetates, hexoates, octoates, ethylhexanoates, and naphthenates. Other suitable transition metal complexes include the acetylacetonates and the hexafluoroacetylacetonates. More preferably, the transition metal compound is selected from the group consisting of copper acetylacetonate, copper ethylhexanoate, copper acetate, copper naphthenate, copper octoate, copper hexoate, and copper hexafluoroacetylacetonate. Most preferably, the transition metal compound is copper acetylacetonate.
- Preferred adhesion promoters include amino silanes, such as gamma-aminopropyltrimethoxy silane, gamma-aminopropyltriethoxy silane, N-(betaaminoethyl)-gamma-aminopropyltriethoxy silane, and the like. However, other organo silanes can be utilized as well as the corresponding silanols and polysiloxanes.
- An example of accelerator/adhesion promoter adhesion promoter solution, or activator sizing agent, includes copper acetylacetonate (2% w/w) and gamma-aminopropyltrimethoxy silane (1%) in methylene chloride. Lower concentrations of both the accelerator and adhesion promoter were found to be effective. The preferred range for the accelerator component is 0.2 to 5% weight in solution. The preferred range for the adhesion promoter is 0.1 to 3 percent by weight in solution.
- Additional preferred embodiments utilize an anaerobic primer system to improve adhesion to cured composite substrates. The primer was designed to interact with the cured composite substrate to improve adhesion. In addition, it increases the cure rate of the anaerobic matrix resin at the interface. During practical use, the primer is applied to the prepared substrate before the impregnated repair plies are applied. The carbon fiber in the repair plies will already contain the metal activating sizing agent to promote rapid cure. The primer will also contain a metal activating cure promoter to increase the cure rate at the interfaces between the cured laminate and the repair laminate.
- Structural composite sections, where repairs are typically applied, can be considered to be relatively non-polar in nature (compared to some polymers and metals). Polarity of the substrate affects its surface energy, which is what enables the matrix resin to wet out the substrate. Clearly, the more the matrix resin is able to wet out, the surface area penetrated is increased and better adhesion achieved. Preferred embodiments of the primer include a solvent, one or more acrylate based resin materials, one or more additional elastomeric materials, and a catalyst of accelerator including a transition metal. The solvent may include tertiary butyl acetate, for substrate wetting, and the one or more acrylate based resin materials may include monomers and/or oligomers derived from, for example, hydroxypropyl methacrylate, isobornyl methacrylate, hexafunctional aromatic urethane acrylate, and methacrylic acid. These acrylate resin materials function to promote adhesion to the carbon fiber and substrate, increase hydrophobicity, serve as a toughener, and increase reactivity. One or more additional elastomer materials such as chlorsulfonated polyethylene, which functions as a toughener, may also be present. Preferred embodiments of the primer may also include copper ethylhexanoate as a catalyst.
- Each component of preferred embodiments of the primer performs a specific function. The hydroxypropyl methacrylate improves chemical adhesion by a hydrogen bonding mechanism through the hydroxyl groups. Isobornyl methacrylate acts as a diluent, but also improves the thermal properties and adhesion. The methacrylic acid and urethane acrylate are intended to increase reactivity and crosslink density of the cured primer. Finally the copper ethylhexanoate is incorporated to promote the anaerobic cure rate at the bonded interfaces. The primer also incorporates an elastomeric toughener, chlorosulfonated polyethylene, and copper ethylhexanoate to accelerate the anerobic cure rate. The primer can be used in conjunction with matrix resins prepared in accordance with preferred embodiments described herein.
- Preferred embodiments described herein are preferably used as a matrix resin for carbon fiber reinforced composites. The types of carbon fiber that can be used with this resin include unidirectional and woven products. These carbon fiber reinforcements are available from several manufacturers including Toray Industries Inc., Toho Tenax Co. Ltd., U.S., Zoltek Companies Inc., and Hexcel Corp.
- The preferred curing method involves inducing an anaerobic state around the impregnated carbon fiber reinforcement. Some composite fabrication techniques employ vacuum assistance as part of the impregnation and compaction process. The use of vacuum inherently produces an anaerobic state, wherein the materials of the present invention would be viable. Examples of this include vacuum bag molding and resin transfer molding. Other composite fabrication techniques could be modified to introduce an anaerobic state, either by use of vacuum or purging the process equipment or molds with a gas that is oxygen-free.
- Carbon fiber reinforcement cloth used in the following examples was Hexcel style 282 made with AS4 input fiber.
- Combinations of the acrylate monomers and oligomers listed in Table 1 can be used in preferred embodiments of the matrix resin. One particularly advantageous preferred embodiment of a resin formulation is described in Table 2 below. This Example resin system was designated internally as AC-1291. It contains methyl methacrylate, methacrylic acid, epoxy acrylate, tris (2-hydroxyethyl) isocyanurate triacrylate, hexafunctional aromatic urethane acrylate, and isobornyl methacrylate. The curing agent components included saccharin, N,N-dimethylaniline, and cumene hydroperoxide.
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TABLE 2 AC-1291 ACRYLATE RESIN SYSTEM Component % Resin components: Methyl Methacrylate 7.89 Methacrylic Acid 9.86 Epoxy acrylate 42.31 Tris (2-hydroxyethyl) isocyanurate 20.19 triacrylate Isobornyl methacrylate 12.62 Hexafunctional aromatic urethane acrylate 4.89 Curative components: Benzoid sulfimide (Saccharin) 0.79 N,N-Dimethylaniline 0.14 Cumene Hydroperoxide 1.31 Total 100.0 - In an example, HEXCEL (Stamford, Conn.) HEXTOW IM7 carbon fiber was treated with a solution of gamma aminopropyltrimethoxy silane (1% w/w) and copper acetylacetonate (2% w/w) dissolved in methylene chloride. The solvent was allowed to evaporate from the carbon fiber, thus leaving an activated sizing component on the reinforcement. Eighteen strands of the treated carbon fiber reinforcement were then pulled into a thin flexible tube. The tube was then injected with the anaerobic epoxy acrylate resin (AC-1291), while fixtured in a dynamic mechanical analyzer (DMA). The dynamic modulus of the composite was measured at room temperature until no additional increase in modulus was observed.
FIG. 1 shows the cure study results, the anaerobic cure profile for AC-1291 resin system with IM7 carbon fiber (2% promoter on fiber) at 73° F. - The cure rate was found to be very rapid when the copper acetylacetonate accelerator concentration in the fiber treatment was 2 percent, showing a cure onset of approximately 3 minutes. The specimen achieved full cure at room temperature within one hour of combining the anaerobic resin and activating carbon fiber fabric. After ambient temperature cure the glass transition temperature for this composite was determined to be 360° F. (182° C.) using DMA in the flexural mode.
- Because of the rapid cure observed at room temperature with the two percent accelerator treatment, additional tests were performed using a range of promoter concentrations (0.008% to 0.25%.)
FIG. 2 shows the effect of varying promoter level (applied to fiber) on level of cure at 73° F. for AC-1291, which is expressed as conversion relative to the ultimate modulus on the plot. - EXAMPLE 3
- Woven carbon fiber fabric (HEXCEL HEXTOW AS4) was pretreated with a sizing containing 0.5 percent copper acetylacetonate accelerator and 1.0 percent gamma aminopropyltrimethoxy silane (adhesion promoter) dissolved in methylene chloride. After evaporation of the solvent, five plies of the woven carbon fiber fabric were impregnated with resin AC-1291 and debulked/cured in a vacuum bag for thirty minutes. The laminate which was approximately 4 inches square was allowed to cure for thirty minutes under vacuum. The exotherm was measured with a thermocouple and the maximum temperature recorded was 65° C. Larger panels were subsequently prepared using this same process.
- Fabrication of larger test laminates was performed for evaluation of composite mechanical and thermal properties. The resin used for these trials was the preferred anaerobic resin AC-1291. No heating blankets were required and the laminate was simply cured by removal of oxygen during the vacuum bagging procedure. The AS4 carbon fiber was treated with the activator sizing agent (0.2% copper acetylacetonate (accelerator) and 1.0% gamma aminopropyltrimethoxy silane dissolved in methylene chloride. In this case the CuAcAC concentration was reduced to 0.2% in order to provide additional working time and to reduce excess exotherm.
- The resin maintained a low viscosity during the lay-up process. After pulling a vacuum on the part (25 in. Hg.) The temperature of the laminate began to increase as the anaerobic reaction was initiated. The maximum temperature measured from the exotherm was approximately 65° C. The ability to fabricate laminates up to 0.20 inches thick was demonstrated. The photograph in
FIG. 3 shows the composite laminate prepared with the developed resin (AC-1291) and 20 plies of AS4 plain weave carbon fiber fabric.FIG. 4 is a photograph of the cured laminate cross section. - Composite sandwich panels are composed of thin, high strength composite skins separated by and bonded to lightweight honeycomb cores. These structures are commonly repaired on aircraft and require additional steps to ensure that mechanical properties are restored to the damaged area.
- A simulated 0.5 inch thick sandwich panel repair was prepared by cutting a 2.5 in diameter circular area from one of the laminate sides. Five AS4 carbon fiber patches, previously treated with activator, were cut to fill the void, and one final patch was applied that was approximately two inches larger in diameter. Each fabric patch was wet-out with AC-1291 resin. A second simulated repair was performed on a 2.0 inch thick sandwich panel using the same basic materials and process. A photograph of this cured repair after debagging is shown in
FIG. 5 . - Laminate repair simulations were performed using previously prepared epoxy/carbon fiber flat panels, 3 ft.×1 ft.×0.168 in. An 8-inch diameter circular area was abraded in the middle of each panel, using a 90 degree die grinder and Scotchbrite pads. Plain weave AS4 carbon fiber cloth, that was previously treated with activator (0.2%), then cut into circular repair plies.
- The circular plies were used to lay-up two simulated repairs, using a “wedding cake” stack configuration to simulate surface doubler repairs. For actual repairs, a tapered scarf repair would typically be done, with the repair plies laid with the smallest ply down first, then the next smallest ply, and so on, with the largest ply being the top repair ply. The reason that the lay-up was prepared in reverse order, with the large ply first and the smallest ply on the top, was to make each repair ply visible during fatigue testing of the cured repair section.
- The previously abraded composite area was wet out with the AC-1291 resin, followed by laying the 7-inch diameter ply into the wet resin and additional resin on top of the ply, using the stiff short-bristle brush to work the resin down through the thickness of the ply. After thoroughly wetting out the first ply, additional resin was applied to wet out the subsequent ply. This process was repeated for all succeeding plies, with the 1-inch circular ply being applied last. Care was taken to ensure that all plies were thoroughly saturated with resin. All plies were laid up as symmetrical 0°/90° plain weave plies, to match the original structure.
- The two sets of repair plies were wet out in the same way, from the same batch of mixed resin. Up to this point, the two repairs were treated identically. The difference between the two repair panels involved the vacuum bag bleeder schedules used.
Panel 1 was bagged with an aggressive bleeder schedule, designed to pull out excess resin under vacuum. - Both parts (
Panels 1 and 2) were connected to a vacuum pump at separate times.Panel 1 was connected to vacuum approximately 30 minutes prior to vacuum being applied toPanel 2. The vacuum pressure was maintained at 24 in Hg to extract air from both bags.Panel 1 was under full vacuum for 3 hours, andPanel 2 was under full vacuum for 2.5 hours. No thermal cure was required. When the panels were debagged, the resin appeared to be fully cured, and was hard to the touch, with no trace of tackiness. - After debagging both panels, it was noted that
Panel 2 had a more resin rich surface compared toPanel 1. This was attributed to the more conservative bleeder schedule used forPanel 2. Photographs of the cured repair laminates are shown inFIG. 6 . - Interlaminar shear strength (ILSS) tests were performed according to ASTM Test Method D2344, Standard Test Method for Short-Beam Strength of Polymer Matrix Composite Materials and Their Laminates (astm.org/Standards/D2344.htm). Specimens were prepared using the AC-1291 resin system with IM7 carbon fiber reinforcement that was previously treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane. The carbon fiber was wet-out using AC-1291 anaerobic resin.
- Forty two ends of the IM7 carbon tow wet-out with AC-1291 resin. The wetted fiber bundle was the pultruded through an enclosed metal die tubing section which removed oxygen availability from the resin. This induced the anaerobic cure conditions. The specimens' were allowed to cure at ambient temperature for 24 hours. After cure, the unidirectional laminate was extracted from the metal tubing and was cut into smaller specimens which were 1.0 in×0.17 in×0.17 in.
- The individual ILSS specimens were positioned in an Instron test machine in a three point bend configuration. Support span was 0.63 inches, and the crosshead speed was 0.05 inches per minute. The maximum load was used to calculate the interlaminar shear strength.
-
FIG. 7 shows short beam shear results for IM7 unidirectional composite prepared with anaerobic resin AC-1291. The data presented inFIG. 7 shows that the AC-1291 matrix resin can deliver strengths comparable to laminates prepared with the standard EA-9390 matrix resin. An average ILSS of 8,570 psi was obtained. - Flexural properties were determined for the anaerobically cured composite prepared with 20 plies of AS4 carbon fiber fabric. The fabric was treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane. The carbon fiber was wet-out using AC-1291 anaerobic resin. A vacuum bag assembly was used to remove oxygen from the bagged laminate to promote cure. Vacuum was maintained for one hour at ambient temperature.
- Four-point bend flexural tests were performed using composite specimens cut from test panel. Specimens having dimensions of 8 in.×0.5 in×0.20 in were used. The support span was six inches and the load span was 3 inches. A crosshead speed of 0.36 inches per minute was used to stress the specimens to failure. The flexural tests were performed at ambient temperature and humidity conditions according to ASTM D6272, Standard Test Method for Flexural Properties of Unreinforced and Reinforced Plastics and Electrical Insulating Materials by Four-Point Bending (astm.org/Standards/D6272). Based on the test results, the AC-1291 resin system was determined to provide acceptable flexural strength and modulus as shown by the data in Table 3.
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TABLE 3 Flexural Strength And Moduli Results For Plain Weave AS4 Carbon Fiber Laminates Prepared With AC-1291 Matrix Resin Sample 1 Sample 2Sample 3 L (support span, in.) 6.1 6.1 6.1 b (sample width, in.) 0.511 0.502 0.54 d (sample thickness, in.) 0.188 0.188 0.188 Modulus msi 9.4 9.4 9.2 Modulus GPa 65 65 63 Max Stress, ksi 68 67 67 Max Stress, Mpa 468 464 460 - Lap-Shear Strength—The level of adhesion of the anaerobic matrix resin to cured composite laminates was determined. One inch wide strips were cut from a previously cured carbon fiber reinforced (CFR) composite which was prepared with AC-1291 resin and 10 plies of AS4 carbon fiber fabric. The fabric was treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane. The carbon fiber was wet-out using AC-1291 anaerobic resin. A vacuum bag assembly was used to remove oxygen from the bagged laminate to promote cure. Vacuum was maintained for one hour at ambient temperature. Cured specimens having dimensions of 6 in.×1 in.×0.10 in. were cut from the resulting laminate panel.
- The cured one-inch wide composite strips were abraded with 120 grit sandpaper followed by cleaning by wiping with methyl ethyl ketone. The cleaned strips were then treated with a methylene chloride primer solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane. After allowing the primer to dry for one hour, AC-1291 anaerobic resin was applied to a one square inch area of each cured laminate strip adherend. A fiberglass scrim cloth was applied to maintain the bondline thickness to 0.010 inches. Two of the strips were then adhered to each other over the one square inch area. The anaerobic cure was allowed to proceed for twenty four hours. After cure, the samples were tested for lap-shear adhesion on an Instron test machine.
- The lap-shear tests were performed according to ASTM D5868 Standard Test Method for Lap Shear Adhesion for Fiber Reinforced Plastic (FRP) (astm.org/Standards/D5868). The results for the tests, which were performed at 73° F., with a crosshead speed of 0.05 inches per minute, are described in Table 4. The average lap-shear strength observed was 1,451 psi.
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TABLE 4 Lap-Shear Strength Test Results; Carbon Fiber/Epoxy Substrates Bonded with AC-1291 Anaerobic MatrixResin Lap Shear Strength Specimen (psi) 1 1,302 2 1,518 3 1,456 4 1,473 5 1,506 AVG 1,451 STD 87 CV % 6 - Dynamic mechanical analysis testing was performed to determine the mechanical properties of cured laminates over a temperature range. Specimens were prepared with anaerobic resin (AC-1291) and treated AS4 plain weave carbon fiber fabric. A composite panel was prepared with AC-1291 resin and 10 plies of AS4 carbon fiber fabric. The fabric was treated with a methylene chloride solution containing 0.2 percent copper acetylacetonate and 1 percent gamma aminopropyltrimethoxysilane. The carbon fiber was wet-out using AC-1291 anaerobic resin. A vacuum bag assembly was used to remove oxygen from the bagged laminate to promote cure. Vacuum was maintained for one hour at ambient temperature. Cured specimens having dimensions of 1.2 in.×0.4 in.×0.1 in. were cut from the resulting laminate panel.
- Cured specimens were oscillated at a rate of 1 Hz in the single cantilever DMA mode while ramping the temperature at a rate of 10° C./min. (5.5° F./min.).
FIG. 8 shows the DMA results obtained, or the glass transition temperature for the AC-1291 resin system reinforced with AS4 carbon fiber (2% promoter on fiber). For comparison, a similar composite was prepared and tested using EA-9390 conventional epoxy matrix resin as shown inFIG. 9 .FIG. 9 shows dynamic mechanical analyses results for EA-9390 resin reinforced with AS4 carbon fiber; Tg after cure at 250° F. (121° C.). The glass transition temperature observed for the anaerobic was comparable to that of the composite fabricated with a standard HENKEL (Bay Point, CA) HYSOL EA-9390 resin, a two-component epoxy adhesive designed for composite repair. Both test laminates exhibited Tg's of approximately 360° F. (182° C.). - Thermogravimetric analysis (TGA) was performed using a TA Instruments Model 2950 Analyzer. Samples of the composites prepared as described in [0062]. However, the specimens for TGA tests were cut to dimensions of 0.1 in.×0.1 in.×0.1 in. Specimens were placed in a tared platinum pan and heated at a rate of 10° C. per minute (5.5° F. per minute) to 600° C. (1,112° F.). The tests were performed in a nitrogen atmosphere.
FIG. 10 shows thermal stability of AC-1291 Resin and standard EA-9390 epoxy resin composites; 20 ply construction with AS4 plain weave carbon fiber fabric. The weight loss plots inFIG. 10 compare the thermal stability of the AC-1291 resin and the standard EA-9390 epoxy resin composites. The onset of thermal decomposition was approximately 800° F. for both the developmental resin and the standard resin. The weight percent fiber reinforcement remaining after elimination of the resin fractions is indicated on the plot as well. These weight percents translate into fiber volume percentages in the range of 48-55%. - Void content testing of the composites was determined according to ASTM D2734, Standard Test Methods for Void Content of Reinforced Plastics (astm.org/Standards/D2734). The measured density of composite specimens was determined by the dry/wet weight method ASTM D792 Method A, Standard Test Methods for Density and Specific Gravity (Relative Density) of Plastics by Displacement (astm.org/Standards/D792). Specimens prepared according to the procedure described in [0054] for preparation of ILSS specimens. Specimens measuring 1.0 in×0.17 in×0.17 in. were weighed in air then weighed when immersed in distilled water at 23° C. Density was then calculated. After the actual density of the composite was determined, the resin fraction was removed using an isothermal thermogravimetric technique. The resin content was then calculated as a weight percent from TGA. By comparing the actual density to the theoretical density, void content was then calculated. Table 5 lists the resin, fiber, and void volume percents for AC-1291 and EA-9390 laminates prepared with AS4 plain weave carbon fiber. The percent void content was 0.35% for the AC-1291 laminate and 5.43% for the EA-9390 laminate. This difference in void content between the laminates can be seen visually in the photomicrographs in
FIG. 11 andFIG. 12 .FIG. 11 shows photomicrographs of AC-1291/AS4 20 ply composite cross sections.FIG. 12 shows photomicrographs of EA-9390/AS4 20 ply composite cross sections. The composite prepared with EA-9390 had a significantly higher level of porosity compared to the AC-1291 laminate. -
TABLE 5 Resin, Fiber, and Void Volume Percents for AC-1291 and EA-9390 Laminates Prepared With AS4 Plain Weave Carbon Fiber Densities (g/cc) EA-9390 1.00 AC-1291 1.05 Carbon Fiber 1.79 AC-1291 Resin EA-9390 20 Ply AS4 20 Ply AS4 Laminate Laminate Wt % Fiber 62.00 68.00 Wt % Resin 38.00 32.00 Vol. of Fiber (cc) 34.64 37.99 Vol. of Resin (cc) 36.19 32.00 Total Volume 70.83 69.99 Vol % Fiber 48.90 54.28 Total Wt 100.00 100.00 Total Volume 70.83 69.99 Theoretical Density 1.41 1.43 Measured Density 1.41 1.35 % Voids 0.35 5.43 - Tables 6 and 7 below provide details regarding the exemplary primer formulation and matrix resin formulations that were prepared and evaluated.
-
TABLE 6 Primer Formulation 5562 Component Function % Solvent (5050 TBAC) Substrate wetting 49.86 Hydroxypropyl methacrylate Promotes adhesion to 23.93 (HPMA) carbon fiber and substrate Chlorosufonated Polyethylene Toughener 11.97 (CSPE) Isobornyl methacrylate (SR-423A) Increases hydrophobicity 5.98 Hexafunctional Aromatic Urethane Toughener 5.98 Acrylate Oligomer (CN-975) Methacrylic acid (MAA) Increases reactivity 1.99 Copper Ethylhexanoate (CEHN) Catalyst 0.28 Total 100.00 -
TABLE 7 Matrix Resin Formulation AC-5911 Component Function Weight % Epoxy acrylate Primary monomer for strength 34.98 Tricyclodecane Dimethanol Improves toughness and 15.56 Diacrylate adhesion Tris (2-hydroxyethyl) Enhances glass transition 15.56 isocyanurate triacrylate temperature Methacrylic Acid Diluent and Tg enhancer 15.56 Methacrylate-functional Toughener 10.49 butadiene copolymer with 21.5% acrylonitrile Hydroxypropyl methacrylate Improves adhesion to carbon 4.90 fiber Benzoic sulfimide Anaerobic Cure promoter 1.05 Cumene Hydroperoxide Catalyst 1.70 Dimethylaniline Cure accelerator 0.20 Total 100.00 - The ambient temperature curing behavior of anaerobic matrix resin AC-5911 was determined by impregnating IM7-12K carbon fiber tow, which was previously sized with a dilute solution of the promoter/silane adhesion promoter. The sizing agent solution was applied to the carbon fiber and allowed to dry leaving residual promoter on the reinforcement. Eighteen strands of the reinforcement were then wet-out with the resin, then fixtured in a dynamic mechanical analyzer (DMA). The dynamic modulus of the composite was measured at room temperature until no additional increase in modulus was observed.
FIG. 13 shows the results for the anaerobic cure profile at 73° F. for AC-5911 Resin System/IM7 Carbon Fiber (2% promoter on fiber). This resin system achieved full cure at room temperature within one hour of fabrication. After ambient cure the glass transition temperature for this composite was determined to be 377° F. (192° C.) using DMA in the flexural mode, as shown inFIG. 14 . This Tg is significantly higher compared to previous matrix resins developed. - Lap Shear Testing. To simulate an actual repair patch, a carbon fiber ply was impregnated with anaerobic matrix resin AC-5911 and sandwiched between two composite substrate pieces that had been previously primed with Primer 5562. The primer, described in Table 6 above, was applied to the solvent wiped substrates. Hexcel style 282 fabric made with AS4 input fiber was then wet-out with anaerobic matrix resin AC-5911, and applied directly to the primed specimens. The specimens were cured anaerobically for 24 hours prior to testing. A crosshead displacement rate of 0.05 inches per minute was used with a sampling rate of 10 points per second. The results obtained were a significant improvement compared to the previous lap-shear data, as shown in Table 8 below.
-
TABLE 8 Comparison of Lap Shear Test Results for Primer 5562 and Matrix Resin AC-5911 Adhering CFRP Laminates Primer None 5562 Matrix Resin AC-1291 AC-5911 Lap Shear Strength (psi) Spec. 1 1,302 1,833 2 1,518 2,020 3 1,456 2,150 4 1,473 1,779 5 1,506 2,313 AVG 1,451 2,019 STD 87 221 CV % 6 11 - Interlaminar Shear Strength Tests. Interlaminar shear strength (ILSS) was determined according to ASTM Test Method D 2344. This test, commonly known as the short-beam strength (SBS) test, attempts to quantify the interlaminar (out-of-plane) shear strength of parallel fiber reinforced composites. Table 9 below contains the ILSS data obtained with composite specimens prepared with matrix resin AC-5911. The substitution of the polybutadiene dimethacrylate with polybutadiene acrylonitrile dimethacrylate significantly increased the ILSS compared to the previously tested anaerobic resin compositions.
-
TABLE 9 Interlaminar shear strength Results for Laminates Prepared with Matrix Resin AC-5911 Laminar Shear Strength (ksi) Spec. 1 10.01 2 10.11 3 9.04 4 9.12 5 10.13 Mean: 9.68 Stnd. Dev. 0.55 CV % 5.71 - Tensile Property Tests. Tensile testing was performed on composite specimens prepared with matrix resin formulation AC-5911 according to ASTM D-638. Five test specimens were tested. The crosshead speed for loading of tensile specimens was 0.2 inches per minute. Based on the results obtained, shown in Table 10 below, resin system AC-5911 appears to be more than adequate in terms of the delivered composite tensile strength.
-
TABLE 10 Tensile Strength Results for Composite Specimens Prepared with Matrix Formulation AC-5911 Specimen Stress at Break Number (ksi) 1 149.13 2 144.04 3 154.46 4 144.97 5 153.58 AVG 149.24 STD 4.78 CV % 3.20
Claims (10)
1. A method for repairing a composite material having a damaged region, comprising:
treating at least a portion of the damaged region of the composite material with a primer to produce a primer-treated damaged region;
pre-treating a reinforcement matrix with an activator sizing agent by applying a solution of the activator sizing agent to the reinforcement matrix and allowing the reinforcement matrix to dry, whereby the reinforcement matrix is coated with a residual coating of organometallic compounds, to produce a pre-treated reinforcement matrix;
sizing the pre-treated reinforcement matrix to an appropriate size for application to the primer-treated damaged region;
placing the pre-treated reinforcement matrix on the primer-treated damaged region;
impregnating the pre-treated reinforcement matrix with an anaerobically curing matrix resin, wherein the anaerobically curing matrix resin contacts the primer in the primer-treated damaged region, wherein the anaerobically curing matrix resin comprises acrylate based resin materials and curing agents, and wherein the curing agents comprise peroxide initiators, aromatic amine accelerators, and benzoic sulfimide, to form a pre-cured composite matrix resin at the primer-treated damaged region; and
exposing the pre-cured composite matrix resin to anaerobic conditions, to form an anaerobically cured composite matrix resin to repair the damaged region of the composite material.
2. The method of claim 1 , wherein the reinforcement matrix is carbon fiber, fiberglass, or quartz.
3. The method of claim 1 , wherein the activator sizing agent is copper acetylacetonate and gamma-aminopropyltrimethoxy silane dissolved in methylene chloride.
4. The method of claim 1 , wherein the acrylate based resin materials comprise tricyclodecane dimethanol diacrylate, methacrylic acid, epoxy acrylate, tris (2-hydroxyethyl) isocyanurate triacrylate, polybutadiene acrylonitrile dimethacrylate, hydroxypropyl methacrylate, and combinations thereof.
5. The method of claim 1 , wherein the peroxide initiators comprise cumene hydroperoxide, t-butylhydroperoxide, p-methane hydroperoxide, diisopropylbenzene hydroperoxide, pinene hydroperoxide, methyl ethyl ketone peroxide, and combinations thereof.
6. The method of claim 1 , wherein the aromatic amine accelerators comprise N,N-diethyl-p-toluidine, N,N-dimethyl-o-toluidine, acetyl phenylhydrazine, N,N-dimethylaniline, N,N-dimethyl-p-toluidine, N,N-dimethyl-p-anisidine, N,N-diethylaniline, N,N-bis-(2-hydroxyethyl)-p-toluidine, and combinations thereof.
7. The method of claim 1 , wherein the elastomeric toughener comprises chlorosulfonated polyethylene.
8. The method of claim 1 , wherein the catalyst is copper ethylhexanoate.
9. The method of claim 1 , wherein the matrix resin consists of tricyclodecane dimethanol diacrylate, methacrylic acid, epoxy acrylate, tris (2-hydroxyethyl) isocyanurate triacrylate, polybutadiene acrylonitrile dimethacrylate, hydroxypropyl methacrylate, benzoic sulfimide, dimethylaniline, and cumene hydroperoxide.
10. The method of claim 1 , wherein the primer consists of tertiary butyl acetate, hydroxypropyl methacrylate, chlorosulfonated polyethylene, isobornyl methacrylate, hexafunctional aromatic urethane acrylate, methacrylic acid, and copper ethylhexanoate.
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